E474 (14.09%) (e474-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E474 (14.09%) (e474-il) Reynolds number: 200,000 Max Cl/Cd: 51.53 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e474-il-200000-n5.txt Download as CSV file: xf-e474-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E474 (14.09%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -1.0645 0.08676 0.08168 -0.0250 1.0000 0.0573
-16.500 -1.0869 0.07986 0.07464 -0.0286 1.0000 0.0587
-16.250 -1.1091 0.07320 0.06787 -0.0320 1.0000 0.0597
-16.000 -1.1339 0.06627 0.06084 -0.0357 1.0000 0.0606
-15.750 -1.1579 0.05951 0.05396 -0.0393 1.0000 0.0618
-15.500 -1.1776 0.05347 0.04779 -0.0425 1.0000 0.0630
-15.250 -1.1931 0.04824 0.04242 -0.0452 1.0000 0.0646
-15.000 -1.2037 0.04395 0.03799 -0.0471 1.0000 0.0665
-14.750 -1.2106 0.04048 0.03436 -0.0482 1.0000 0.0687
-14.500 -1.2193 0.03725 0.03105 -0.0487 1.0000 0.0707
-14.250 -1.2237 0.03479 0.02850 -0.0483 1.0000 0.0734
-14.000 -1.2237 0.03291 0.02649 -0.0473 1.0000 0.0762
-13.750 -1.2219 0.03133 0.02479 -0.0459 1.0000 0.0792
-13.500 -1.2212 0.02986 0.02329 -0.0440 1.0000 0.0821
-13.250 -1.2166 0.02870 0.02204 -0.0421 1.0000 0.0858
-13.000 -1.2090 0.02774 0.02095 -0.0400 1.0000 0.0894
-12.750 -1.2048 0.02677 0.01997 -0.0375 1.0000 0.0928
-12.500 -1.1973 0.02599 0.01913 -0.0350 1.0000 0.0969
-12.250 -1.1873 0.02532 0.01834 -0.0326 1.0000 0.1011
-12.000 -1.1808 0.02464 0.01766 -0.0296 1.0000 0.1049
-11.750 -1.1684 0.02407 0.01701 -0.0274 1.0000 0.1097
-11.500 -1.1546 0.02350 0.01635 -0.0254 1.0000 0.1141
-11.250 -1.1417 0.02296 0.01581 -0.0232 1.0000 0.1183
-11.000 -1.1264 0.02248 0.01524 -0.0212 1.0000 0.1226
-10.750 -1.1102 0.02199 0.01465 -0.0194 1.0000 0.1266
-10.500 -1.0954 0.02153 0.01419 -0.0173 1.0000 0.1304
-10.250 -1.0788 0.02112 0.01372 -0.0154 1.0000 0.1345
-10.000 -1.0609 0.02072 0.01319 -0.0137 1.0000 0.1386
-9.750 -1.0444 0.02029 0.01278 -0.0118 1.0000 0.1422
-9.500 -1.0269 0.01993 0.01238 -0.0099 1.0000 0.1461
-9.250 -1.0084 0.01959 0.01195 -0.0083 1.0000 0.1504
-9.000 -0.9899 0.01923 0.01152 -0.0066 1.0000 0.1542
-8.750 -0.9719 0.01889 0.01119 -0.0048 1.0000 0.1579
-8.500 -0.9530 0.01860 0.01084 -0.0031 1.0000 0.1620
-8.250 -0.9332 0.01830 0.01044 -0.0016 1.0000 0.1662
-8.000 -0.9142 0.01797 0.01010 0.0001 1.0000 0.1697
-7.750 -0.8949 0.01768 0.00982 0.0017 1.0000 0.1734
-7.500 -0.8749 0.01742 0.00949 0.0032 1.0000 0.1775
-7.250 -0.8543 0.01717 0.00914 0.0047 1.0000 0.1814
-7.000 -0.8345 0.01686 0.00886 0.0062 1.0000 0.1849
-6.750 -0.8142 0.01661 0.00860 0.0077 1.0000 0.1886
-6.500 -0.7934 0.01638 0.00833 0.0090 1.0000 0.1926
-6.250 -0.7722 0.01617 0.00804 0.0104 1.0000 0.1964
-6.000 -0.7516 0.01589 0.00779 0.0118 1.0000 0.1999
-5.750 -0.7309 0.01567 0.00758 0.0131 1.0000 0.2037
-5.500 -0.7096 0.01547 0.00736 0.0144 1.0000 0.2077
-5.250 -0.6636 0.01532 0.00712 0.0108 0.9938 0.2128
-5.000 -0.6191 0.01503 0.00691 0.0073 0.9860 0.2179
-4.750 -0.5742 0.01480 0.00669 0.0040 0.9784 0.2236
-4.500 -0.5326 0.01458 0.00641 0.0013 0.9704 0.2286
-4.250 -0.4962 0.01427 0.00618 -0.0003 0.9621 0.2335
-4.000 -0.4564 0.01402 0.00595 -0.0025 0.9547 0.2393
-3.750 -0.4233 0.01380 0.00571 -0.0033 0.9445 0.2444
-3.500 -0.3890 0.01351 0.00548 -0.0044 0.9336 0.2493
-3.250 -0.3556 0.01326 0.00527 -0.0053 0.9197 0.2553
-3.000 -0.3249 0.01305 0.00504 -0.0054 0.9006 0.2613
-2.750 -0.2928 0.01277 0.00481 -0.0060 0.8746 0.2669
-2.500 -0.2533 0.01251 0.00451 -0.0078 0.8304 0.2742
-2.250 -0.2165 0.01235 0.00416 -0.0088 0.7594 0.2817
-2.000 -0.1908 0.01240 0.00396 -0.0079 0.6896 0.2890
-1.750 -0.1673 0.01251 0.00383 -0.0066 0.6298 0.2961
-1.500 -0.1444 0.01260 0.00373 -0.0054 0.5764 0.3040
-1.250 -0.1211 0.01270 0.00366 -0.0043 0.5287 0.3132
-1.000 -0.0975 0.01277 0.00360 -0.0033 0.4879 0.3238
-0.750 -0.0734 0.01281 0.00356 -0.0024 0.4544 0.3352
-0.500 -0.0490 0.01285 0.00353 -0.0016 0.4269 0.3478
-0.250 -0.0244 0.01287 0.00351 -0.0008 0.4023 0.3629
0.000 0.0000 0.01288 0.00350 0.0000 0.3809 0.3810
0.250 0.0244 0.01287 0.00351 0.0008 0.3629 0.4022
0.500 0.0490 0.01285 0.00353 0.0016 0.3478 0.4268
0.750 0.0734 0.01281 0.00356 0.0024 0.3351 0.4544
1.000 0.0975 0.01277 0.00360 0.0033 0.3238 0.4880
1.250 0.1211 0.01270 0.00366 0.0043 0.3133 0.5285
1.500 0.1444 0.01260 0.00373 0.0054 0.3040 0.5762
1.750 0.1673 0.01251 0.00383 0.0066 0.2961 0.6296
2.000 0.1909 0.01240 0.00396 0.0079 0.2891 0.6894
2.250 0.2165 0.01235 0.00416 0.0088 0.2818 0.7593
2.500 0.2532 0.01250 0.00451 0.0078 0.2743 0.8298
2.750 0.2927 0.01276 0.00481 0.0060 0.2669 0.8744
3.000 0.3250 0.01305 0.00504 0.0054 0.2612 0.9006
3.250 0.3555 0.01326 0.00527 0.0053 0.2554 0.9198
3.500 0.3890 0.01351 0.00548 0.0044 0.2493 0.9336
3.750 0.4233 0.01380 0.00571 0.0033 0.2444 0.9445
4.000 0.4564 0.01402 0.00595 0.0025 0.2393 0.9548
4.250 0.4961 0.01427 0.00618 0.0003 0.2335 0.9621
4.500 0.5326 0.01458 0.00641 -0.0014 0.2286 0.9704
4.750 0.5743 0.01480 0.00669 -0.0040 0.2235 0.9785
5.000 0.6193 0.01503 0.00691 -0.0074 0.2179 0.9861
5.250 0.6637 0.01532 0.00712 -0.0108 0.2128 0.9939
5.500 0.7096 0.01547 0.00736 -0.0144 0.2077 1.0000
5.750 0.7308 0.01567 0.00758 -0.0131 0.2037 1.0000
6.000 0.7516 0.01589 0.00779 -0.0118 0.1999 1.0000
6.250 0.7721 0.01616 0.00803 -0.0104 0.1964 1.0000
6.500 0.7934 0.01638 0.00833 -0.0090 0.1926 1.0000
6.750 0.8142 0.01661 0.00860 -0.0076 0.1886 1.0000
7.000 0.8344 0.01686 0.00885 -0.0062 0.1848 1.0000
7.250 0.8542 0.01717 0.00914 -0.0046 0.1814 1.0000
7.500 0.8748 0.01742 0.00949 -0.0032 0.1774 1.0000
7.750 0.8949 0.01768 0.00981 -0.0017 0.1734 1.0000
8.000 0.9142 0.01796 0.01010 -0.0001 0.1697 1.0000
8.250 0.9332 0.01830 0.01044 0.0016 0.1662 1.0000
8.500 0.9529 0.01860 0.01084 0.0031 0.1620 1.0000
8.750 0.9719 0.01889 0.01119 0.0048 0.1579 1.0000
9.000 0.9899 0.01923 0.01152 0.0066 0.1543 1.0000
9.250 1.0084 0.01959 0.01195 0.0083 0.1505 1.0000
9.500 1.0269 0.01993 0.01238 0.0099 0.1462 1.0000
9.750 1.0444 0.02029 0.01278 0.0118 0.1422 1.0000
10.000 1.0609 0.02072 0.01319 0.0137 0.1387 1.0000
10.250 1.0789 0.02112 0.01372 0.0154 0.1345 1.0000
10.500 1.0955 0.02153 0.01419 0.0173 0.1304 1.0000
10.750 1.1103 0.02199 0.01465 0.0193 0.1266 1.0000
11.000 1.1265 0.02248 0.01524 0.0212 0.1227 1.0000
11.250 1.1419 0.02296 0.01581 0.0231 0.1183 1.0000
11.500 1.1548 0.02350 0.01635 0.0253 0.1142 1.0000
11.750 1.1687 0.02406 0.01701 0.0274 0.1098 1.0000
12.000 1.1810 0.02464 0.01766 0.0295 0.1049 1.0000
12.250 1.1876 0.02532 0.01833 0.0325 0.1009 1.0000
12.500 1.1978 0.02598 0.01912 0.0349 0.0967 1.0000
12.750 1.2052 0.02676 0.01996 0.0374 0.0927 1.0000
13.000 1.2093 0.02774 0.02095 0.0400 0.0893 1.0000
13.250 1.2173 0.02869 0.02203 0.0420 0.0857 1.0000
13.500 1.2218 0.02985 0.02327 0.0439 0.0821 1.0000
13.750 1.2226 0.03132 0.02478 0.0458 0.0792 1.0000
14.000 1.2245 0.03289 0.02648 0.0472 0.0763 1.0000
14.250 1.2245 0.03477 0.02848 0.0482 0.0732 1.0000
14.500 1.2203 0.03722 0.03102 0.0486 0.0707 1.0000
14.750 1.2116 0.04046 0.03433 0.0481 0.0686 1.0000
15.000 1.2049 0.04391 0.03794 0.0470 0.0665 1.0000
15.250 1.1943 0.04820 0.04238 0.0451 0.0645 1.0000
15.500 1.1789 0.05343 0.04775 0.0424 0.0629 1.0000
15.750 1.1589 0.05952 0.05397 0.0391 0.0616 1.0000
16.000 1.1359 0.06614 0.06071 0.0356 0.0606 1.0000
16.250 1.1113 0.07304 0.06770 0.0319 0.0597 1.0000
16.500 1.0884 0.07984 0.07462 0.0284 0.0585 1.0000
16.750 1.0667 0.08661 0.08152 0.0249 0.0573 1.0000
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Polar data table (+)
Polar graphs
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